Wireless communication system within an external enclosure for attachment to a vehicle

ABSTRACT

Disclosed herein are systems for routing wireless communications. Some systems may include an apparatus comprising an enclosure configured to attach to an external portion of an aircraft and which may contain: a wireless communications device, and an antenna in communication with the wireless communications device and configured to send or receive signals to and/or from aircraft.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims priority to U.S. Provisional Patent App. No.62/873,548, filed on Jul. 12, 2019, which is incorporated herein byreference in its entirety.

TECHNICAL FIELD

The subject matter described herein generally relates to improvingcommunications between aircraft and other ground, air, or space-basedentities. For example, certain disclosed embodiments are directed to anapparatus for routing wireless communications to and/or from anaircraft. Embodiments also include routing wireless communications fromthe aircraft above and below an aircraft. This apparatus may have aparticular shape, angling, installation location, and/or combination ofparts allowing for effective communication to and from an aircraft. Theapparatus may also be configured to attach to an aircraft. In somecases, such an apparatus may transmit and receive communications to atransmitter and/or receiver using existing electric power wiring.

BACKGROUND

Modern aircraft have important needs for communication with otherentities, especially ground-based flight coordinators and otheraircraft. Flying has many associated threats, including partmalfunctions, dangerous weather, and even mid-air collision. Effectivecommunication to and from aircraft navigating the skies is crucial tomitigating these threats and thereby improving safety of aircraftpassengers, pilots, and entities on the ground.

Conventional systems typically rely on one or more antennas and atransponder inside the aircraft to receive, transmit, and processvarious data communications. Some of these data communications mayinclude those sent according to the ADS-B (Automatic DependentSurveillance-Broadcast) standard. However, as communication demands onaircraft have increased, existing systems have not always kept pace tomeet these needs in an efficient, reliable, and cost-effective manner.

Moreover, conventional aircraft are increasingly expected to communicatenot only with ground-based communications entities and other aircraft,but also with satellites. Existing systems on aircraft may be challengedby effectively communicating, simultaneously in some cases, withsatellites, other aircraft, and ground-based systems due to the antennasavailable on the aircraft, the antenna locations, or the availablesurface area to install antennas not balancing desirable positioning forline-of-sight communications while simultaneously reducing interferenceto or from other antennas for other systems on the aircraft. Forexample, some aircraft may only have an antenna that is best suited toonly communicate with a subset of these entities, while sacrificingcommunications to others. Retrofitting an aircraft with datacommunications wiring, new exterior access points, and new antennae maybe enormously complex and cost-prohibitive for many aircraft andtherefore does not present a viable solution. Moreover, suchretrofitting may be complicated to implement and may involve significantchanges depending on the aircraft being modified.

In view of the technical deficiencies of current systems, there is aneed for an apparatus that can be easily and cost-effectively installedto an aircraft without causing significant modifications to the aircraftas it currently exists, while optimizing communication line-of-sightpaths to ground, air, and space-based entities. The apparatus discussedbelow offers many technological improvements in efficiency, usability,and cost savings. For example, according to one embodiment, a singleapparatus may be configured for installation on a wing or tail of anaircraft, which may allow for communication with both surveillancesatellites as well as ground-based systems without requiring twoseparate antennae. Moreover, this apparatus may be integrated withaircraft-position and anti-collision lighting, which may leverageexisting aircraft wiring and mounting locations.

Related advantages may result from disclosed embodiments that integratea communications device (e.g., a transponder) and an antenna into asingle apparatus. Such embodiments may allow for installation ofmultiple components simultaneously, reducing the complexity and cost ofinstallation.

Further, some disclosed embodiments allow for an apparatus that may haveunique antenna placement and angling, which may allow for more reliablecommunications with ground, air, and space objects. And, in somedisclosed embodiments, the apparatus may communicate to componentsinside an aircraft by using direct wiring (e.g., serial, coaxial, CAT-5,optical, etc.) and/or wireless signaling. In some cases, the apparatusmay use existing electrical wiring to improve ease of integration intothe aircraft.

SUMMARY

Some disclosed embodiments describe an apparatus for routing wirelesscommunications. For example, the apparatus may include an enclosureconfigured to attach to an external portion of an aircraft andcontaining: a wireless communications device, and an antenna incommunication with the wireless communications device and configured tosend or receive signals to or from the aircraft.

In accordance with further embodiments, the enclosure is configured toattach to an external lighting interface of the aircraft.

In accordance with further embodiments, the apparatus may furthercomprise further comprising a light, wherein: the light is one of anavigation light, anti-collision light, rear-position light, rotatingbeacon light, or landing light.

In accordance with further embodiments, the enclosure is configured toattach to one of a wing or tail of the aircraft.

In accordance with further embodiments, the enclosure is configured toallow a light to attach to the enclosure.

In accordance with further embodiments, the wireless communicationsdevice comprises a transponder.

In accordance with further embodiments, the enclosure is configured toattach to an external lighting interface of the aircraft.

In accordance with further embodiments, the apparatus is configured tosend signals to, or receive signals from, above and below the aircraft.

In accordance with further embodiments, the antenna is a dipole antennaconfigured to send signals to, or receive signals from, above and belowthe aircraft.

In accordance with further embodiments, the apparatus further comprisesa light, wherein: the light is one of a navigation light, anti-collisionlight, rear-position light, rotating beacon light, or landing light.

In accordance with further embodiments, the enclosure is configured toattach to one of a wing or tail of the aircraft.

In accordance with further embodiments, the enclosure is configured toallow a light to attach to the enclosure.

In accordance with further embodiments, the transponder is configured tosend and/or receive an ADS-B signal.

In accordance with further embodiments, the enclosure contains a globalnavigation satellite system (GNSS) receiver.

In accordance with further embodiments, the enclosure contains a globalnavigation satellite system (GNSS) antenna.

In accordance with further embodiments, the enclosure contains abarometric altimeter.

In accordance with further embodiments, the enclosure contains a radioantenna.

In accordance with further embodiments, the transponder operatesaccording to one of Modes 1, 2, 3, A, C, S, ES, 4, or 5.

In accordance with further embodiments, the apparatus is configured tosend signals to, or receive signals from, above and below the aircraft.

In accordance with further embodiments, the antenna is a dipole antennaconfigured to send signals to, or receive signals from, above and belowthe aircraft.

In accordance with further embodiments, the antenna is a monopoleantenna.

Further disclosed embodiments include an apparatus for routing wirelesscommunications. For example, the apparatus may comprise: a fin-shapedenclosure configured to attach to an external portion of an aircraft andcontaining: a wireless communications device, and an antenna incommunication with the wireless communications device and configured tosend or receive signals from above or below the aircraft.

In accordance with further embodiments; the wireless communicationsdevice comprises a transponder.

In accordance with further embodiments, the enclosure is configured toattach to a wing of the aircraft.

In accordance with further embodiments, the enclosure is configured toattach to a tail of the aircraft.

In accordance with further embodiments, the enclosure is configured toattach to a fuselage of the aircraft.

In accordance with further embodiments, the antenna is a dipole antenna.

In accordance with further embodiments, the enclosure comprises at leasttwo protruding fins containing the dipole antenna.

In accordance with further embodiments, the enclosure includes at leastone protruding fin that is canted toward a rear side of the aircraftwhile the enclosure is attached to the aircraft.

In accordance with further embodiments, the at least one protruding finis canted toward the rear side of the aircraft at an angle of between 5and 60 degrees relative to a vertical axis.

In accordance with further embodiments, the angle is based on at leastone of: a model of the aircraft, a shape of a fuselage of the aircraft,a size of a fuselage of the aircraft, a shape of a wing of the aircraft,or a size of a wing of the aircraft.

In accordance with further embodiments, the enclosure includes at leastone protruding fin that is canted away from a fuselage of the aircraftwhile the enclosure is attached to the aircraft.

In accordance with further embodiments, the at least one protruding finis canted away from the fuselage of the aircraft at an angle of between5 and 60 degrees relative to a vertical axis.

In accordance with further embodiments, the angle is based on at leastone of: a model of the aircraft, a shape of a fuselage of the aircraft,a size of a fuselage of the aircraft, a shape of a wing of the aircraft,or a size of a wing of the aircraft.

In accordance with further embodiments, the enclosure is composed of asignal interference-reducing material.

In accordance with further embodiments, the enclosure is composed of aplastic.

In accordance with further embodiments, the enclosure is coated in aheat-resistant, low-friction coating.

Aspects of the disclosed embodiments may include tangiblecomputer-readable media that store software instructions that, whenexecuted by one or more processors, are configured for and capable ofperforming and executing one or more of the methods, operations, and thelike consistent with the disclosed embodiments. Also, aspects of thedisclosed embodiments may be performed by one or more processors thatare configured as special-purpose processor(s) based on softwareinstructions that are programmed with logic and instructions thatperform, when executed, one or more operations consistent with thedisclosed embodiments.

It is to be understood that both the foregoing general description andthe following detailed description are exemplary and explanatory only,and are not restrictive of the disclosed embodiments, as claimed.

BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying drawings, which are incorporated in and constitute apart of this specification, illustrate several embodiments and, togetherwith the description, serve to explain the disclosed principles. In thedrawings:

FIG. 1A illustrates an exemplary pictographic representation of awireless communications apparatus.

FIG. 1B illustrates an exemplary schematic representation of a firstwireless communications system.

FIG. 10 illustrates an exemplary schematic representation of a secondwireless communications system.

FIG. 2A illustrates an exemplary pictographic representation of amulti-finned wireless communications apparatus.

FIG. 2B illustrates an exemplary pictographic representation of alighting interface wireless communications apparatus.

FIG. 3 illustrates an exemplary pictographic representation of atail-mountable wireless communications apparatus.

FIG. 4 illustrates an exemplary pictographic representation of a cantedfinned wireless communications apparatus.

FIG. 5 illustrates an exemplary side-view pictographic representation ofa canted wing-attachable wireless communications apparatus.

FIG. 6 illustrates an exemplary frontal-view pictographic representationof a canted wing-attachable wireless communications apparatus.

FIG. 7 illustrates an exemplary pictographic representation of awing-attachable wireless communications apparatus.

DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS

Reference will now be made in detail to exemplary embodiments, examplesof which are illustrated in the accompanying drawings and disclosedherein. Wherever convenient, the same reference numbers will be usedthroughout the drawings to refer to the same or like parts. Thedisclosed embodiments are described in sufficient detail to enable thoseskilled in the art to practice the disclosed embodiments. It is to beunderstood that other embodiments may be utilized and that changes maybe made without departing from the scope of the disclosed embodiments.Thus, the components, materials, methods, and examples are illustrativeonly and are not intended to be necessarily limiting.

FIG. 1A illustrates an exemplary pictographic representation of wirelesscommunications apparatus 10 and other exemplary elements. While thisfigure may describe a context of affixing a wireless communicationsapparatus to a wing (e.g., at a light fixture) of an aircraft, one willappreciate that other configurations are possible, such as the wirelesscommunications apparatus being suited to attach to a tail (e.g., at alight fixture) of an aircraft, a fuselage of an aircraft, or anywhereelse on the aircraft with visibility to devices communicating with thewireless communications apparatus. In some embodiments, wirelesscommunications apparatus 10 may be configured to be mounted usingexisting lighting locations and may use a downward pointing monopoleantenna for optimization of ground and air-based communications. In someembodiments, a wireless communications apparatus 10 may be enclosed byan enclosure 100. In some embodiments, enclosure 100 may be configuredto attach to an external portion of an aircraft, drone, boat, and/orother vehicle. In some embodiments, wireless communications apparatus 10may be configured for attachment to a particular vehicle and/orparticular part of a vehicle, such as to an external lighting interfaceof an aircraft (e.g., a connection point for a Grimes wingtip strobelight). In some embodiments, wireless communications apparatus 10 and/orenclosure 100 may have a shape, size angling, material composition,combination of parts, and/or other configuration that may be based on anaircraft, and/or a particular area of an aircraft, to which it will beattached. For example, enclosure 100 and/or any other part of wirelesscommunications apparatus 10 may be configured to attach to a wing, tail,and/or fuselage of an aircraft. In some embodiments, wirelesscommunications apparatus 10 may be configured to attach parallel to avertical and/or horizontal centerline of an aircraft. To facilitateattachment, enclosure 100 may include a portion shaped for connection toa socket of an aircraft, groves, threads, fastener connection points(e.g., holes for rivets), a snap fastening mechanism, and/or any otherportion with a shape, size, material, flexibility, etc. suitable forattaching to an aircraft. In some embodiments, enclosure 100 may beconfigured to attach to a mounting plate. In other embodiments,enclosure 100 may be configured to attach to another vehicle altogether(e.g., a drone, boat, etc.).

Enclosure 100 may completely or partially enclose components of wirelesscommunications apparatus 10. For example, enclosure 100 may include anopening 112, which may allow for wiring 114 or other objects to passthrough or otherwise access components internal to enclosure 100 (e.g.,a circuit board, processor, memory, sensor, etc.), including humanaccess for maintenance, part upgrades, and the like. Wiring 114 maycomprise any combination of conductive and insulating materialsconfigured to carry power and/or data communications.

Wireless communications apparatus 10 may include a variety ofcomponents, which may be enclosed by enclosure 100. For example,wireless communications apparatus 10 may include a wirelesscommunications device 102. Wireless communications device 102 mayinclude any device configured to process electronic communications, suchas a transponder, a network chip, a processor, a special purposeprocessor, a memory component, and the like. Merely by way of example,such a transponder may be one of, without limitation, a Ping1090i,Ping2020i, Ping200S/Si/Sr, Ping20Si, Ping200X, or other type oftransponder. In some embodiments, such as where wireless communicationsdevice 102 includes a transponder, it may be configured to send and/orreceive an ADS-B signal and/or may operate using at least one of Modest2, 3, A, C, S, ES, 4, or 5. In some embodiments, a signal (e.g., anADS-B signal) sent or received by wireless communications device 102 maybe vertically polarized.

In some embodiments, wireless communications device 102 may connect toan antenna 104, which may send and/or receive wireless communications.For example, antenna 104 may be configured to send and/or receivesignals to and/or from an aircraft, which may be sent and/or receivedfrom above and/or below an aircraft. Similarly, antenna 104 may beconfigured to allow communication with ground-based systems or satellitesystems. In some embodiments, antenna 104 may be a dipole or a monopoleantenna, which may be configured to send and receive signals to or fromabove and/or below the aircraft.

Wireless communications sent and received by an antenna 104 may passthrough enclosure 100, which may be made of any of a variety ofmaterials, including, but not limited to, such as plastic, fiberglass,metal, etc., which may be used to reduce signal interference. Forexample, an aircraft or a ground communications station may send and/orreceive a signal to/from wireless communications apparatus 10, and thesecommunications may be sent and/or received through antenna 104. In someembodiments, antenna 104 may be positioned within a fin-shaped portionof an enclosure 100, as shown in an exemplary fashion in FIG. 1A. Forexample, enclosure 100 may be conformed to a configuration suitable fora dipole and/or monopole antenna. Conforming the shape of enclosure 100to the position, size, and/or shape of antenna 104 may reduce the amountof material needed to manufacture wireless communications apparatus 10,may improve aerodynamic qualities of wireless communications apparatus10, and/or may improve the signaling quality of wireless communicationsapparatus 10. Antenna 104 may route information it has received towireless communications device 102, which may in turn route informationreceived to a computing and/or display device within an aircraft (e.g.,a display within a cockpit of an aircraft).

Wireless communications apparatus 10 may also include a light 106.Enclosure 100 may be configured such that light 106 may be visible fromoutside of enclosure 100. For example, light 106 may be positioned onthe exterior of enclosure 100, within or through an opening in enclosure100, or within enclosure 100 (e.g., with at least a portion of enclosure100 being at least translucent to allow for the light 106 to be seenexternally from enclosure 100). Light 106 may be a navigation light,anti-collision light, rear-position light, rotating beacon light, orlanding light, or any light configured to illuminate to notify observers(e.g., aircraft, autonomous devices, human observers on the ground,devices on the ground, etc.) as to the position, speed, shape, size,and/or dimensions of a vehicle to which wireless communicationsapparatus 10 may be attached, such as an aircraft. By way of example andwithout limitation, light 106 may be a halogen lamp, a strobe light,and/or an LED light. In some embodiments, wireless communicationsapparatus 10 may include multiple lights 106, and each light may have adifferent purpose (e.g., one light may be an anti-collision light, andanother light may be a landing light). In some embodiments, light 106may be configured to remain lit, flash, pulse, and/or alter itsintensity. These actions may be controlled by a user (e.g.: byactivating a switch that causes a signal to be sent to light 106 andcontrol its behavior) and/or a contextual state of wirelesscommunications apparatus 10 or a vehicle to which wirelesscommunications apparatus 10 may be attached (e.g., airborne, travelingat a threshold speed, surrounded by level of air pressure meeting athreshold, presence in an environment having visibility meeting athreshold, a current time of day, etc.). For example, a light 106, whichmay be an anti-collision light, may be configured to flash only when anaircraft is airborne and/or airborne above a certain altitude. Asanother example, a light 106 may be configured to automatically activate(be lit, pulse, etc.) when natural light in an environment of anaircraft is below a certain threshold (e.g., indicating that it may beafter sunset or before sunrise). Such aspects of an aircraft'scontextual state may be determined by other devices and/or sensorswithin the aircraft (e.g., an altimeter), and/or components and/orsensors within wireless communications apparatus 10 (e.g., a lightsensor). In some embodiments, enclosure 100 may be configured to allowlight 106 to attach to the enclosure (discussed further with respect toFIG. 2B). For example, enclosure 100 may include a socket or otherinterface to which a light 106 may connect. By having light 106integrated into wireless communications apparatus 10, functionality maybe added to an aircraft (e.g. transponder functions on a wingtip) whilestill preserving lighting for navigation, position, anti-collisionpurposes etc. For example, light 106 may operate simultaneously withother components of wireless communications apparatus 10, such aswireless communications device 102 and/or communications unit 108.

System 10 may also include a communications unit 108, which may includea GPS chip, radio chip, WiFi chip, and/or any other processing componentfor wireless communications. In some embodiments, communications unit108 may be subordinate to wireless communications device 102 (e.g.,wireless communications device 102 may have central processing priorityfor communications routed within system 10). Communications unit 108 mayalso be enclosed by enclosure 100. Communications unit 108 may beconfigured to send and/or receive communications different from thosesent and/or received by wireless communications device 102. For example,communications unit 108 may include a processor for processingcommunications such as radio signals. As another example, communicationsunit 108 may include a global navigation satellite system (GNSS)receiver and/or transceiver (e.g., contained by enclosure 100), forprocessing signals received from, and/or to be sent to, a satellite.Communications unit 108 may connect to an antenna 104 (a radio antenna,a GNSS antenna, etc.), which may be configured to send and/or receivesignals, which may be routed to and/or from communications unit 108(radio signals, GNSS signals, etc.). In some embodiments, communicationsunit 108 may process information received before routing it. As anotherexample communications unit 108 may re-format GPS information into aformat suitable for display (e.g., at a control head). By integratingcommunications unit 108, wireless communication system 10 may be able toprovide additional functionalities beyond those that may be offered bywireless communications device 102, together in a single attachableunit. In some embodiments, communications unit 108 may connect to anantenna 110, which may send and/or receive communications (e.g., GPScommunications) that are different from those sent and/or received bywireless communications device 102. In some embodiments, antenna 110 maybe configured to receive a certain type of communication. For example,antenna 110 may be a monopole or dipole antenna. Antenna 110 may alsohave a particular length, shape, position, canting, and/or any othercharacteristic for maintaining reliable communications.

In some embodiments, communications unit 108 may include a sensor, suchas a barometric altimeter, an air pressure sensor, a humidity sensor, alight sensor, an accelerometer, drone remote identification detector,etc. A sensor may detect particular contextual aspects (e.g., altitude,air pressure, humidity level, amount of light, visibility, speed, etc.)of wireless communications apparatus 10 and/or a vehicle to whichwireless communications apparatus 10 may be attached. In someembodiments, communications unit 108 may include an altitude encoder.

Communications unit 108 may also include a control interface (e.g., forcommunicating with a control head). The interface may communicate withexternal components, such as a control head, via differentcommunications channels. For example, the system may use a powerlinemodem, which my communicate data over wiring 114, or an RS232 line.Communications unit 108 may also be configured to communicate withexternal components via WiFi. In some embodiments, communications unit108 may be configurable by another device (e.g., by a mobile device,such as an iOS or Android device, connected to wireless communicationsapparatus 10 over WiFi, which may be achieved through aconfigurable-over-WiFi control interface). For example, a mobile devicemay execute an application that allows the mobile device to connect to(e.g., over WiFi) and configure wireless communications apparatus 10.For example, a user interacting with a user interface of such anapplication may input, change, and/or delete information of, withoutlimitation: a call sign, an International Civil Aviation Organization(ICAO) number, a maximum aircraft speed, a Vso, an ADS-B In capability,an ADS-B Out capability, an emitter type, an aircraft length, a GPSantenna lateral offset, a GPS antenna longitudinal offset, and/or anyother information that may be used by wireless communications apparatus10. Any of this information may also be automatically populated by theapplication based on information stored on wireless communicationsapparatus 10 (e.g., in a memory component). Based on inputs received atthe application, wireless communications apparatus 10 may determineinformation to transmit (e.g., to other aircraft, to ground stations,etc.). Wireless communications apparatus 10 may also include any numberof components discussed with respect to FIGS. 1B and 1C.

FIG. 1B illustrates an exemplary schematic representation of a firstwireless communications system 120, which may be a constitute all or aportion of any of the apparatuses described herein. For example,components of first wireless communications system 120 may be part of awireless communications apparatus 10. First wireless communicationssystem 120 may include a baseband section 122 and a power radiofrequency (RF) section 124. First wireless communications system 120 mayinclude any or all of the exemplary components shown in FIG. 1B.

First wireless communications system 120 may include components that aredesignated, in this example, as part of baseband section 122. In someembodiments, first wireless communications system 120 may include apower supply 128, which may receive power from aircraft power 126 (e.g.,a source of power within an aircraft, which may exist separately from awireless communications apparatus 10). In some embodiments, firstwireless communications system 120 may include an input-output (I/O)protection circuit 138, which may connect to a control interface 136,which may be separate from a wireless communications apparatus 10. I/Oprotection circuit 138 may connect to a processor 148 (e.g., afield-programmable gate array or FPGA, application-specificationintegrated circuit or ASIC, other integrated circuit, etc.), which mayexecute a program containing instructions for carrying out processeswithin first wireless communications system 120. For example, processor148 may implement a transponder. Processor 148 may send and/or receivedata to and/or from control interface 136. I/O protection circuit 138may receive input from control interface 136 and route the input toprocessor 148, while protecting the system from dangerous or impropersignals. First wireless communications system 120 may also include abarometer 140, which may sense barometric pressure values, which may betransmitted to processor 148. First wireless communications system 120may also include a receiver 142, which may receive signals from atransmit-receive (T/R) switch 132, which may be part of power RE section124 (described below). In some embodiments, first wirelesscommunications system 120 may include an input protection circuit 146,which may connect to a position and/or altitude interface 144, which mayallow processor 148 to send and/or receive data to and/or from positionand/or altitude interface 144. Input protection circuit 146 may receiveinput from position and/or altitude interface 144 and route the input toprocessor 148, while protecting the system from dangerous or impropersignals, processor 148 may carry out any number of processes, such asthose described herein (e.g., processing transponder communications,processing communications for configuration sent over WiFi).

First wireless communications system 120 may also include componentsthat are designated, in this example, as part of power RE section 124.Those components may include a transmitter 130, which may receive powerfrom power supply 128, and may connect to processor 148 and may transmitsignals over antenna 134. Transmitter 130 may be a transmitter fortransmitting 1090 Mhz RF signals, including 1090 MHz replies to ATCRBSand Mode S interrogations.

In some embodiments, first wireless communications system 120 mayinclude a transmit-receive (T/R) switch 132 that is connected toTransmitter 130, Receiver 142, and Antenna 134. T/R Switch 132 mayconnect Transmitter 130 and Receiver 142 to a shared antenna. T/R Switch132 operates to switch the connection of the antenna to Transmitter 130or Receiver 142 to allow communicate with the antenna when transmittingor receiving, respectively. Receiver 142 may receive 1030 MHz signals,including 1030 MHz ATCRBS and Mode S interrogations.

FIG. 1C illustrates an exemplary schematic representation of a secondwireless communications system 160, which may be a constitute all or aportion of any of the apparatuses described herein. For example,components of second wireless communications system 160 may be animplementation of a wireless communications apparatus 10 alternative tofirst wireless communications system 120. Second wireless communicationssystem 160 may include any or all of the exemplary components shown inFIG. 1C.

Second wireless communications system 160 may include a device 162(e.g., a wireless communications apparatus 10). Aircraft power 164(e.g., a source of power within an aircraft, which may exist separatelyfrom a wireless communications apparatus 10) may supply power to device162. In some embodiments, aircraft power 164 may connect to a powersupply 166, which may be part of device 162.

Device 162 may include a number of components, such as those shown inexemplary FIG. 1C. For example, device 162 may include a transponder176, which may connect to at least one other component, and which mayperform functions of a transponder, consistent with disclosedembodiments. Transponder 176 may connect to and receive power from powersupply 166. In some embodiments, transponder 176 may connect tobarometric pressure sensor 168, which may detect measurements ofbarometric pressure (e.g., in the environment of an aircraft to whichdevice 162 may be attached) and transmit measurements to transponder176. Device 162 may also include a control interface 170, which mayconnect to transponder 176 and control head 172, which may be separatefrom device 162 (e.g., a control head within a fuselage of an aircraft,which may be accessible from a cockpit of an aircraft). In someembodiments, transponder 176 may transmit 1090 Mhz RF signals (e.g.,using antenna 182), including 1090 MHz replies to ATCRBS and Mode Sinterrogations. In some embodiments, transponder 176 may receive 1030MHz signals (e.g., using antenna 182), including 1030 MHz ATCRBS andMode S interrogations.

In some embodiments, device 162 may include a GPS component 174, whichmay receive power from power supply 166. GPS component 174 may beconnected to GPS antenna 178, which may receive signals from otherdevices (e.g., a GPS constellation) and may route signals to GPScomponent 174. GPS component 174 may process received signals and maytransmit signals to transponder 176, to which GPS component 174 may beconnected.

Other components may also be included in device 162 and may connect totransponder 176. For example, device 162 may include a WiFi component180, antenna 182 (e.g., antenna 104), and/or light 184 (e.g., light106). WiFi component 180 may be configured to connect to an externaldevice (e.g., mobile device) over WiFi, which may allow forconfiguration and/or information transmission, as discussed with respectto FIG. 1A. Antenna 182, which may be an antenna 104, may send and/orreceive wireless communications, such as transponder communications(e.g., ADS-B signals). Light 184 may include any or all of thecapabilities of light 106, discussed with respect to FIG. 1A.

FIG. 2A illustrates an exemplary pictographic representation of amulti-finned wireless communications apparatus 20, which may includecharacteristics of wireless communications apparatus 10. For example,multi-finned wireless communications apparatus 20 may include anenclosure 200 (i.e., similar to enclosure 100), which may be configuredto attach to a vehicle, such as to a wing of an aircraft. In someembodiments, multi-finned wireless communications apparatus 20 may beconfigured to be mounted using existing wingtip lighting locationsand/or may use an upward and/or downward pointing dipole antenna foroptimization of ground, air, and space-based communications. In otherembodiments, enclosure 200 may be configured to attach to a tail orfuselage of an aircraft. Multi-finned wireless communications apparatus20 may also include components 202, which may include a sensor,processor, memory, antenna, transponder, and/or component discussed withrespect to FIGS. 1A, 1B, and/or 1C (e.g., a GNSS receiver).

Multi-finned wireless communications apparatus 20 may include anantenna, such as a dipole antenna 204 with two portions, antenna portion204 a and antenna portion 204 b. Antenna 204 may connect to thecomponents 202, which may include a wireless communications device(e.g., a transponder). In some embodiments, antenna portion 204 a and/orantenna portion 204 b may send and/or receive wireless communications.For example, antenna portion 204 a and/or antenna portion 204 b may beconfigured to send and/or receive signals to and/or from an aircraft,ground stations, or satellite systems. Such signals may be sent and/orreceived from above and/or below an aircraft. In other embodiments, amonopole antenna may be used and may be contained within an upward ordownward angled fin.

As with enclosure 100 and wireless communications apparatus 10,enclosure 200 and/or any other part of multi-finned wirelesscommunications apparatus 20 may be particularly configured toaccommodate and/or enhance the capabilities of antenna portion 204 aand/or antenna portion 204 b. For example, enclosure 200 may have aparticular shape (e.g., a dual-fin shape), which may allow for theplacement of antenna portion 204 a and/or antenna portion 204 b withinmulti-finned wireless communications apparatus 20 while preserving orenhancing its aerodynamic properties.

In some embodiments, antenna portion 204 a may be angled predominantlyupward, and antenna portion 204 b may be angled predominantly downward.In this way, multi-finned wireless communications apparatus 20 may allowfor more reliable wireless electronic communications to receivers aboveand/or below an aircraft. In some embodiments, antenna portion 204 a andantenna portion 204 b may be part separate antennas that may alternatetransmissions, achieving antenna diversity. Multi-finned wirelesscommunications transponder apparatus 20 may also include any number ofcomponents discussed with respect to FIGS. 1B and 10.

FIG. 2B illustrates a lighting interface wireless communicationsapparatus 206, which may be an instance of multi-finned wirelesscommunications apparatus 20, tail-mountable wireless communicationsapparatus 30, or any other attachable apparatus described herein,consistent with disclosed embodiments. In some embodiments, lightinginterface wireless communications apparatus 206 may be configured toallow a light to attach to an enclosure of lighting interface wirelesscommunications apparatus 206 (e.g., as discussed with respect to FIG.1A). For example, lighting interface wireless communications apparatus206 may include a recessed region 208, which may have a particularconfiguration (size, shape, material, rigidity, etc.) allowing a light(e.g., light 106), or component including a light, to attach to anenclosure of lighting interface wireless communications apparatus 206(e.g., an enclosure 200). For example, recessed region 208 may have aparticular shape that allows a component including a light to snap orlatch onto an enclosure of lighting interface wireless communicationsapparatus 206.

FIG. 3 illustrates an exemplary pictographic representation of atail-mountable wireless communications apparatus 30, which may includeany or all of the characteristics of wireless communications apparatus10. For example, tail-mountable wireless communications apparatus 30 mayinclude an enclosure 300 (i.e., similar to enclosure 100), which may beconfigured to attach to a vehicle, such as to a tail of an aircraft. Insome embodiments, tail-mountable wireless communications apparatus 30may be configured to be mounted using existing tail lighting locationsand may use an upward and/or downward pointing dipole antenna foroptimization of ground, air, and space-based communications.Tail-mountable wireless communications apparatus 30 may also includecomponents 302, which may include a sensor, processor, memory, antenna,transponder, and/or component discussed with respect to FIGS. 1A, 1B,and/or 1C (e.g., a GNSS receiver).

Similar to wireless communications apparatus 10, tail-mountable wirelesscommunications apparatus 30 may include an antenna 304. Antenna 304 mayalso be the same as or similar to antenna 204, including portions 204 aand 204 b forming a dipole antenna. In some embodiments, antenna 304 maysend and/or receive communications to and/or from any of components 302,such as a transponder.

Like wireless communications apparatus 10, tail-mountable wirelesscommunications apparatus 30 may be configured to allow wiring 306 topass through enclosure 300, such as to connect to components 302 (e.g.,a circuit board, processor, memory, sensor, etc.) internal to enclosure300. Wiring 306, like wiring 114, may comprise any combination ofconductive and insulating materials configured to carry power and/ordata communications.

Tail-mountable wireless communications apparatus 30 may also include alight 308, which may share any or all of the same characteristics aslight 106, discussed with respect to FIG. 1A. For example, light 308 maybe a navigation light, anti-collision light, rear-position light,rotating beacon light, or landing light, or any light configured toilluminate to notify observers (e.g., aircraft, autonomous devices,human observers on the ground, devices on the ground, etc.) as to theposition, speed, shape, size, and/or dimensions of a vehicle to whichwireless communications apparatus 30 may be attached, such as anaircraft. Tail-mountable wireless communications apparatus 30 may alsoinclude any number of components discussed with respect to FIGS. 1B and1C.

FIG. 4 illustrates an exemplary pictographic representation of a cantedfinned wireless communications apparatus 40, which may include any orall of the characteristics of wireless communications apparatus 10. Forexample, canted finned wireless communications apparatus 40 may includean enclosure 400 (i.e., similar to enclosure 100), which may beconfigured to attach to a vehicle, such as to a tail of an aircraft. Insome embodiments, enclosure 400 may be composed of a signalinterference-reducing material. Enclosure 400 may be composed of anumber of materials, including a plastic, metal, polycarbonate,fiberglass, etc. In some embodiments, enclosure 400 may be coated with aheat-resistant and/or low-friction coating, which may enhanceaerodynamic properties of canted finned wireless communicationsapparatus 40 and/or may decrease a rate of degradation the system mayexperience over time.

Canted finned wireless communications apparatus 40 may also includecomponents (not shown), which may include a sensor, processor, memory,antenna, transponder, and/or component discussed with respect to FIGS.1A, 1B, and/or 1C (e.g., a GNSS receiver). For example, canted finnedwireless communications apparatus 40 may include any device configuredto process electronic communications, such as a transponder (e.g., aPing200X transponder), a network chip, a processor, a special purposeprocessor, a memory component, and the like. For example, canted finnedwireless communications apparatus 40 may also include any number ofcomponents discussed with respect to FIGS. 1B and 1C. Canted finnedwireless communications apparatus 40, similar to wireless communicationsapparatus 10, may be configured to attach to a wing, tail, and/orfuselage of an aircraft.

While canted finned wireless communications apparatus 40 may share anyor all characteristics of wireless communications apparatus 10, it mayalso include other desirable features. In some embodiments, cantedfinned wireless communications apparatus 40 may include a fin, which maybe a protruding portion of enclosure 400. For example, canted finnedwireless communications apparatus 40 may include a fin 402 a, which maybe disposed on a top portion of canted finned wireless communicationsapparatus 40. In some embodiments, canted finned wireless communicationsapparatus 40 may have a sub-fin 402 b, which in some embodiments may bea portion of a larger fin structure, as shown in an exemplary fashion inFIG. 4. For example, sub-fin 402 b may be a smaller fin that protrudesfrom a larger fin, which may be disposed on a bottom portion of cantedfinned wireless communications apparatus 40, as shown in an exemplaryfashion in FIG. 4. In some embodiments, canted finned wirelesscommunications apparatus 40 with a sub-fin 402 b may allow for improvedsignaling in space-based systems. In other embodiments, canted finnedwireless communications apparatus 40 may only have a fin or fins that donot have any number of sub-fins. Thus, canted finned wirelesscommunications apparatus 40 may include any number of fins 402 a andsub-fins 402 b.

In some embodiments, canted finned wireless communications apparatus 40may include a fin that encloses (e.g., with enclosure 400) a monopoleantenna. In other embodiments, canted finned wireless communicationsapparatus 40 may include at least two fins containing a dipole antenna(similar to the exemplary depiction in FIG. 2). In some embodiments, anantenna may be contained within a fin and/or a sub-fin.

Canted finned wireless communications apparatus 40 may include a finand/or sub-fin that may be canted in a particular fashion. For example,in some embodiments, enclosure 400 may include at least one protrudingfin that is canted toward a rear side of an aircraft while enclosure 400is attached to the aircraft. A solely exemplary visual depiction of aprotruding fin that is canted toward a rear side of an aircraft is shownin FIG. 5. Canting an antenna may shift the axis of the antenna awayfrom a vertical axis. For example, this may improve signaling to and/orfrom above and/or below an aircraft by shifting the “dead zone” of theantenna away from the vertical axis. This may be advantageous whencommunicating with satellites that are positioned nearly verticallyoverhead.

As a further example, a fin may be canted toward the rear side of anaircraft at an angle of between 5 and 60 degrees relative to a verticalaxis, though any number of degrees of canting may be used. An angle ofcanting may be based on at least one of: a model of the aircraft, ashape of a fuselage of the aircraft, a size of a fuselage of theaircraft, a shape of a wing of the aircraft, or a size of a wing of theaircraft. For example, an aircraft having a smaller wing to which acanted finned wireless communications apparatus 40 is attached may havea fin canted to a smaller degree than an aircraft having a larger wing.Canting an antenna (i.e., within a fin) toward the rear of an aircraftmay reduce signal interference of communications sent to and/or from acomponent in canted finned wireless communications apparatus 40, and/ormay also have beneficial aerodynamic properties (e.g., relative to anon-canted system) for a vehicle (e.g., aircraft) to which canted finnedwireless communications apparatus 40 may be attached.

In some embodiments, enclosure 400 may include at least one protrudingfin that may be canted away from a fuselage of the aircraft while theenclosure is attached to the aircraft. A solely exemplary visualdepiction of a protruding fin that may be canted toward a rear side ofan aircraft is shown in FIG. 6. As a further example, fin may be cantedaway from the fuselage of the aircraft at an angle of between 5 and 60degrees relative to a vertical axis, though any number of degrees ofcanting may be used. An angle of canting may be based on at least oneof: a model of the aircraft, a shape of a fuselage of the aircraft, asize of a fuselage of the aircraft, a shape of a wing of the aircraft,or a size of a wing of the aircraft. As with canting an antenna towardthe rear of an aircraft, canting an antenna (i.e., within a fin) awayfrom the fuselage of an aircraft may reduce signal interference ofcommunications sent to and/or from a component in canted finned wirelesscommunications apparatus 40, and/or may also have beneficial aerodynamicproperties (e.g., relative to a non-canted system) for a vehicle (e.g.,aircraft) to which canted finned wireless communications apparatus 40may be attached.

Exemplary FIG. 5 further illustrates an exemplary pictographicrepresentation of a protruding fin (e.g., fin 402 a) that is cantedtoward a rear side of an aircraft while a wireless communicationsapparatus 502 (e.g., canted finned wireless communications apparatus 40)is attached to the aircraft 50. In this exemplary depiction, wirelesscommunications apparatus 502 is attached to a wing 500 of the aircraft50. As discussed with respect to FIG. 4, and as depicted in FIG. 5,wireless communications apparatus 502 includes a fin that is cantedtoward the rear of aircraft 50 at an angle 504 with respect to avertical axis (shown by the dashed line).

Exemplary FIG. 6 further illustrates an exemplary pictographicrepresentation of a protruding fin (e.g., fin 402 a) that is canted awayfrom a fuselage of an aircraft while a wireless communications apparatus602 (e.g., canted finned wireless communications apparatus 40) isattached to the aircraft 60. In this exemplary depiction, wirelesscommunications apparatus 602 is attached to a wing 600 of the aircraft60. As discussed with respect to FIG. 4, and as depicted in FIG. 6,wireless communications apparatus 602 includes a fin that is canted awayfrom the fuselage of aircraft 60 at an angle 604 with respect to avertical axis (shown by the dashed line).

FIG. 7 illustrates an exemplary pictographic representation of anaircraft communications system for an aircraft 70, within which awireless communications apparatus may be integrated. In someembodiments, the aircraft communications system may include a wirelesscommunications apparatus 704 (e.g., wireless communications apparatus10, 30, etc.), which may be attached to a wing 702 of aircraft 70.Wireless communications apparatus 704 may be connected to internalelectronic components 708 and/or a power source 710 by wiring 706. Forexample, wiring 706 may carry data communications between wirelesscommunications apparatus 704 and internal electronic components 708,which may include a control head, display, and other components allowinga user to configure or interact with wireless communications apparatus704. In some embodiments, wiring 706 may be initially configured to onlysend power from power source 710 (e.g., intended for a light on a wingof an aircraft), but may be configured to send data communications aswell, by using at least one powerline networking component, such as apowerline modem. For example, a powerline networking component may beincluded within wireless communications apparatus 704 and another may bepart of internal electronic components 708. In other embodiments, wiring706 may include wiring for a data connection (e.g., an RS232 connection)to electronic components 708, such as a control head. In yet otherembodiments, a wireless communications component 704 may communicatewirelessly with internal electronic components 708. These embodimentsmay be achieved with a wireless communications apparatus 704 configuredto attach to a wing of an aircraft as well as a wireless communicationsapparatus 704 configured to attach to a tail of an aircraft.

It is to be understood that the disclosed embodiments are notnecessarily limited in their application to the details of constructionand the arrangement of the components and/or methods set forth in thefollowing description and/or illustrated in the drawings and/or theexamples. The disclosed embodiments are capable of variations, or ofbeing practiced or carried out in various ways.

For example, while some embodiments are discussed in a context involvingaircraft, these elements need not be present in each embodiment. Whileaircraft communications apparatuses and systems are discussed in someembodiments, other electronic systems (e.g., radio communicationsystems) having any kind of wireless communications devices may alsooperate within the disclosed embodiments. Such variations are fullywithin the scope and spirit of the described embodiments.

The descriptions of the various embodiments of the present disclosurehave been presented for purposes of illustration, but are not intendedto be exhaustive or limited to the embodiments disclosed. Manymodifications and variations will be apparent to those of ordinary skillin the art without departing from the scope and spirit of the describedembodiments. The terminology used herein was chosen to best explain theprinciples of the embodiments, the practical application or technicalimprovement over technologies found in the marketplace, or to enableothers of ordinary skill in the art to understand the embodimentsdisclosed herein.

It is appreciated that certain features of the disclosure, which are,for clarity, described in the context of separate embodiments, may alsobe provided in combination in a single embodiment. Conversely, variousfeatures of the disclosure, which are, for brevity, described in thecontext of a single embodiment, may also be provided separately or inany suitable subcombination or as suitable in any other describedembodiment of the disclosure. Certain features described in the contextof various embodiments are not to be considered essential features ofthose embodiments, unless the embodiment is inoperative without thoseelements.

Although the disclosure has been described in conjunction with specificembodiments thereof, it is evident that many alternatives, modificationsand variations will be apparent to those skilled in the art.Accordingly, it is intended to embrace all such alternatives,modifications and variations that fall within the spirit and broad scopeof the appended claims.

1. An apparatus for routing wireless communications, the apparatuscomprising: an enclosure configured to attach to an external portion ofan aircraft, wherein the enclosure: comprises a first portion angledupward and a second portion angled downward; and contains: a wirelesscommunications device, and an antenna in communication with the wirelesscommunications device, the antenna being configured to: send or receivesignals to or from the aircraft; send or receive signals above theaircraft; and send or receive signals below the aircraft.
 2. Theapparatus of claim 1, wherein the enclosure is configured to attach toan external lighting interface of the aircraft.
 3. The apparatus ofclaim 2, further comprising a light, wherein: the light is one of anavigation light, anti-collision light, rear-position light, rotatingbeacon light, or landing light.
 4. The apparatus of claim 3, wherein theenclosure is configured to attach to one of a wing or tail of theaircraft.
 5. The apparatus of claim 2, wherein the enclosure isconfigured to allow a light to attach to the enclosure.
 6. The apparatusof claim 1, wherein the wireless communications device comprises atransponder.
 7. The apparatus of claim 6, wherein the enclosure isconfigured to attach to an external lighting interface of the aircraft.8. (canceled)
 9. The apparatus of claim 7, wherein the antenna is adipole antenna.
 10. The apparatus of claim 7, further comprising alight, wherein: the light is one of a navigation light, anti-collisionlight, rear-position light, rotating beacon light, or landing light. 11.The apparatus of claim 9, wherein the enclosure is configured to attachto one of a wing or tail of the aircraft.
 12. The apparatus of claim 7,wherein the enclosure is configured to allow a light to attach to theenclosure.
 13. The apparatus of claim 6, wherein the transponder isconfigured to send and/or receive an ADS-B signal.
 14. The apparatus ofclaim 13, wherein the enclosure contains a global navigation satellitesystem (GNSS) receiver.
 15. The apparatus of claim 14, wherein theenclosure contains a global navigation satellite system (GNSS) antenna.16. The apparatus of claim 1, wherein the enclosure contains abarometric altimeter.
 17. The apparatus of claim 1, wherein theenclosure contains a radio antenna.
 18. The apparatus of claim 6,wherein the transponder operates according to one of Modes 1, 2, 3, A,C, S, ES, 4, or
 5. 19. (canceled)
 20. (canceled)
 21. The apparatus ofclaim 1, wherein the antenna is a monopole antenna.
 22. The apparatus ofclaim 1, wherein the enclosure is configured to attached to a mountingplate.
 23. The apparatus of claim 1, the apparatus further comprising asensor configured to detect a contextual aspect of the apparatus or theaircraft.